CN104564798B - Piezo-electric damping system for axial turbine rotor - Google Patents
Piezo-electric damping system for axial turbine rotor Download PDFInfo
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- CN104564798B CN104564798B CN201410541360.2A CN201410541360A CN104564798B CN 104564798 B CN104564798 B CN 104564798B CN 201410541360 A CN201410541360 A CN 201410541360A CN 104564798 B CN104564798 B CN 104564798B
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- pzt
- piezoelectric transducer
- circuit
- diameter
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- 238000013016 damping Methods 0.000 title claims abstract description 42
- 238000005452 bending Methods 0.000 claims description 3
- 239000003990 capacitor Substances 0.000 abstract description 9
- 230000005284 excitation Effects 0.000 abstract description 7
- 230000003068 static effect Effects 0.000 description 7
- 230000000694 effects Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 239000002131 composite material Substances 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 210000003323 beak Anatomy 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000010363 phase shift Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/005—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion using electro- or magnetostrictive actuation means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/10—Suppression of vibrations in rotating systems by making use of members moving with the system
-
- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10N—ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10N30/00—Piezoelectric or electrostrictive devices
- H10N30/30—Piezoelectric or electrostrictive devices with mechanical input and electrical output, e.g. functioning as generators or sensors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/11—Purpose of the control system to prolong engine life
- F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/334—Vibration measurements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/60—Control system actuates means
- F05D2270/62—Electrical actuators
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of compressor or the rotors of axial turbine comprising vibration damping system, the vibration damping system are assembled into the PZT (piezoelectric transducer) (28) that round is distributed and is connected to consumption resonance circuit (36).The circuit is closure, and is equipped with resistor and coil.The PZT (piezoelectric transducer) (28) is divided into two groups of alternate energy converters, and every group is connected to passive RLC circuit.In order to ensure the set of its capacitor and electric current, the PZT (piezoelectric transducer) (28) is connected in parallel.In operation, the rotor is subjected to rotation excitation and is likely to vibrate and deform according to the Mode Shape with diameter with deformation wave (30).The number of energy converter is equal to four times of the diameter number of mode, so as to utilize the symmetry of this mode with diameter.The grouping of the PZT (piezoelectric transducer) (28) deformed in the same manner is so that the available same apparatus thus gathered damps the PZT (piezoelectric transducer).
Description
Technical field
The present invention relates to a kind of axial turbine rotors.More particularly it relates to a kind of for damping axial turbine
The system of the vibration of machine rotor.More particularly it relates to a kind of for damping axial turbine rotor to consume circuit
The system of the vibration of impeller.
Background technique
During operation, the heterogeneous stream (annular heterogeneous flow) of annular passes through axial turbine.It is true
On, any object in axial uniform flow can generate the variation of Pneumatic pressure in its ambient enviroment, to make the stream
Unevenly.Wherein, these objects can be blade, shell pillar or variable discharge door.
When the blade of blade rotor rotates in this circumferential heterogeneous annular flow, the unexpected change of each of pressure
Change can be considered as dotted excitation.The excitation number within the scope of 360 ° associated with given rotation speed causes specifically to swash
Encourage frequency.If its intrinsic frequency for corresponding to rotor, rotor can be specific according to being made of a certain number of nodal diameters
Deformation pattern generates resonance.
When blade rotor wheel generates resonance in certain variations model domain, increased level of vibration can be generated.Such as
In the case where integral blade disk or integral type leaf drum, the inherent damping level of structure is weaker, these level of vibration can be bigger.Due to
These level of vibration are associated with high-stress state, this can significantly reduce the fatigue life of structure and may cause structural failure,
So to avoid such level of vibration.In this case, it in order to ensure the fatigue durability of impeller, inevitably uses
Damping device.
In the damping device of blade turbomachine rotor wheel for being subjected to diameter distortion can be envisaged, Piezoelectric Shunt system generation
A kind of interesting scheme of table.It is formed by the piezoelectric patches for being attached to consumption circuit.
Document JP19960861295 discloses a kind of blade rotor, by the pressure being distributed in the rotor peripheral extent
Electric piece reduces the vibration of the blade rotor.Each is connected to the closed circuit including dead resistance device.Operating principle exists
It is present in the same position of piezoelectric patches in deformation, once deformation, the piezoelectric patches just generate the resistor of the circuit by being connected
The electric current of consumption.The damping method makes the vibration that can reduce rotor, and carrys out identical effect to each frequency band.However,
For the vibration with strong amplitude, which is invalid.The system further relates to provide component for each closed circuit, from
And increase quality and cost.It is unfavorable for space needed for assembling each circuit.
Summary of the invention
Technical problem
It is an object of the invention to overcome the problems, such as that the prior art proposes.The purpose of the present invention is
It is modified to the effect of damping the system of the vibration of axial turbine rotor, which, which is presented, has static or rotation diameter mould
Formula.It is another object of the present invention to propose a kind of system for damping the vibration of turbine rotor, the system is in high frequency
It can be same as in low frequency effective.It is another object of the present invention to reduce the system of the vibration for damping turbine rotor
Weight.
Technical solution
The present invention relates to the rotor of a kind of rotor, especially compressor, including vibration damping system, the vibration damping system
System is distributed on the rotor and is connected at least one set of PZT (piezoelectric transducer) of at least one consumption circuit with including into round, shows
Work is characterized in that PZT (piezoelectric transducer) is connected to be consumed each of circuit or consumption circuit and be connected in parallel with set (pool)
At least two energy converters respective sets, the uniform ditch of described group or each group energy converter is distributed on the rotor.
The PZT (piezoelectric transducer) is advantageously arranged to each energy converter can follow institute at the transducer position discussed
It states the deformation of rotor and deforms deviously.
Advantageous embodiment in accordance with the invention, the rotor can be according to Mode Shape (a modal with diameter
Shape with diameters) vibration under deform, the number of described group or each group of PZT (piezoelectric transducer) is equal to the mould
Twice of the diameter number of the state vibration shape.
Advantageous embodiment in accordance with the invention, the Mode Shape with diameter consist essentially of two with nodal diameter
Orthogonality distortion wave, under any circumstance, the PZT (piezoelectric transducer) angle are distributed in two adjacent nodal diameters of two deformation waves
Between.
Term " two adjacent nodal diameters " means two continuous nodal diameters of two deformation waves.One node
Diameter belongs to one in two orthogonality distortion waves, and another nodal diameter belongs to another in two deformation waves.
Advantageous embodiment in accordance with the invention, the damping system include being connected in parallel to corresponding one in consumption circuit
At least two energy converter of multiple groups, the polarity of each group of energy converter connects into when the energy converter deforms in the same direction
When, the energy converter generates the electric current with the same symbol in its corresponding consumption circuit.
Advantageous embodiment in accordance with the invention, the damping system only include one group at least two for being connected to consumption circuit
A, preferably at least four energy converters, the polarity of described group of energy converter are connected into when the energy converter deforms in the same direction
When, the energy converter generates the electric current with the same symbol in the consumption circuit.
Advantageous embodiment in accordance with the invention, the damping system include two group of at least two energy converter, and described group of angle is inclined
All groups of the uniform ditch of all energy converters is moved into be distributed on the rotor.
Advantageous embodiment in accordance with the invention, the rotor can become under the vibration according to the Mode Shape with diameter
Shape, the damping system include two groups of PZT (piezoelectric transducer)s, and two groups of PZT (piezoelectric transducer)s are relative to each other with the revolution (a of sub-fraction
Fraction of revolution) and out-phase, the revolution of the sub-fraction are equal to the Mode Shape with diameter
Four times of inverse of diameter number.
Advantageous embodiment in accordance with the invention, consuming at least one of circuit or consumption circuit includes at least one induction
Device, to form resonance circuit with the energy converter being connected in parallel, at least one of the consumption circuit or consumption circuit are preferably
It is substantially combined with the PZT (piezoelectric transducer) of corresponding group and forms closed circuit.
Advantageous embodiment in accordance with the invention, at least one of the consumption circuit or consumption circuit do not have external electrical
Source.
Advantageous embodiment in accordance with the invention, the rotor have at least one resonance frequency omegaR, the consumption circuit is
Antihunt circuit, preferably resonance circuit, wherein the damped frequency ω of the consumption circuitAIt is humorous equal to the rotor to be damped
Vibration frequency ωR。
Advantageous embodiment in accordance with the invention, the rotor are impeller or leaf drum.
Advantageous embodiment in accordance with the invention, the blade are integrally formed.
Advantageous embodiment in accordance with the invention, the thickness of PZT (piezoelectric transducer) show as more than vane thickness 5%, preferably
30%, more preferably 100%.
Advantageous embodiment in accordance with the invention, at least one of PZT (piezoelectric transducer) be arranged in cylindrical surface or perpendicular to turn
On the surface of the rotation axis of son, it is preferably located in except aerodynamic flow.
Advantageous embodiment in accordance with the invention, the energy converter be arranged to caused by the bending movement as rotor stretching/
The lower deformation of compression, preferably follows the bending deformation of the shell of the rotor.
The invention further relates to a kind of turbines including rotor, are significantly characterized in that, the rotor according to the present invention and
It is formed, and the rotor is preferably the rotor of compressor or the rotor of turbine.
Advantageous embodiment in accordance with the invention, during the operation in critical speed, the rotor is with straight according to having
The resonance frequency of the mode of diameter, the number of each group of PZT (piezoelectric transducer) are greater than or equal to the diameter number of resonance mode
Twice, preferably equivalent to the four of diameter number times.
Advantageously, the PZT (piezoelectric transducer) is identical.
It provides the advantage that
The invention enables the deformation symmetry using blade rotor wheel in the given model domain with diameter.It is logical
It crosses and equably arranges PZT (piezoelectric transducer) within the scope of 360 °, static or rotation vibration mode can be damped.
By the way that PZT (piezoelectric transducer) is divided into two groups and is controlled its polarity, their capacitor can be combined.Rlc circuit
Resonance frequency byIt indicates, the collection credit union of capacitor generates increased equivalent capacity.Therefore, in equal frequencies, inductance
Value can be lower.
The consumer gathers and is used for many PZT (piezoelectric transducer)s.Overall efficacy is enhanced, and for handling
A possibility that reduced frequency, is improved.
Detailed description of the invention
Fig. 1 shows axial turbine according to the present invention.
Fig. 2 is the diagram of the low pressure compressor of the turbine of Fig. 1.
Fig. 3 shows rotor according to the present invention, the rotor according to tool there are two quadrature wave with diameter (in presentation
There are three in example) mode and deform.
Fig. 4 shows vibration damping system according to the present invention.
Fig. 5 shows according to the present invention for consuming the circuit of electric energy.
Specific embodiment
In the following description, the inside and outside position for referring to the rotation axis relative to axial turbine of term.
Fig. 1 shows a kind of axial turbine.In this particular case, the turbine is turbofan.Turbofan 2
Including the first compression stage (referred to as low pressure compressor 4), the second compression stage (referred to as high pressure compressor 6), combustion chamber 8 and one or more
A stage of turbine 10.During operation, the machine power of turbine 10 is transmitted via central axis, and keeps two compressors 4 and 6 mobile.
Speed reduction gearing can increased or decrease the rotation speed for being transmitted to compressor.In another embodiment, turbine is not at the same level
Compressor stage can be connected to via concentric shafts.These axis include many blade rotor wheels separated by stator vane wheel.Leaf
Piece rotor wheel rotates about the rotation of axis 14 so that can produce air-flow, and the air-flow that gradually reduces burns until entering
Until the entrance of room 8.
The entrance ventilator of commonly referred to as fan 16 is connected to rotor 12, and generates and be divided into main stream (primary flow)
18 and Secondary Flow (secondary flow) 20 air-flow, main stream 180 passes through the not at the same level of turbine above-mentioned, secondary
Stream 20 is passed through along the circular passage (being shown partially in) of machine length, to merge at turbine outlet with main stream.Main stream 18
It is annular flow and the shell for being conducted through turbine with Secondary Flow 20.
Fig. 2 is the sectional view of the low pressure compressor 4 of the axial turbine 2 of such as Fig. 1.Herein, it can be seen that fan 16
The separation rostral (separation beak) 22 of a part and main stream 18 and Secondary Flow 20.Rotor 12 includes several rotors
Blade row 24, such as three rows.Low pressure compressor 4 includes several row of stator 26, such as four rows.Rectifier and fan 16 or rotor
Blade row is associated, to adjust the air-flow, thus by the rate conversion of the stream at pressure.
The rotor portion of the low pressure compressor has the cylindrical form of commonly referred to as drum, and rotor blade is fixed on rotor portions
On part.It includes substantially thin outer wall, and thickness may be generally less than 8.00 millimeters, preferably less than 5.00 millimeters, more preferably
Ground is less than 3.00 millimeters.The wall of rotor 12 can have body structure surface axially and/or radially.According to the present invention one
A alternative, the rotor can have the form of integral type disk, and blade is located on the circumference of integral type disk.
It is roused and blade can be made of metal material, such as titanium or aluminium.They can also be made of composite material.They
Size be made into the static stress for bearing certain level, the static stress can generate by centrifugal force, expansion or pressure.It is roused
The dynamic stress generated by its vibratory response has been additionally contemplates that with the vane size.
During operation, rotor 12 can meet with dynamic exciting, and the major part of dynamic exciting is made of air-operated drive.As sound
It answers, rotor can vibrate.The specific run speed of driver or turbine can be vibration source.The structure of turbine can will be another
The vibration of element is transmitted to rotor 12.
Wherein, the vibration of rotor can be observed on its drum and blade.Corresponding to the modality-specific group under given frequency
At described vibrate makes the wall of the drum generate axially and/or radially deformation and/or circumferential deformation.For integral blade disk or one
Formula leaf drum, structural damping are still very low.Level of vibration and associated dynamic therefore, which constrain, can become problem.In fact, quality increases
Benefit make it necessary to the wall of the drum/integral blade disk is thinning, to reduce its intensity and rigidity.
In order to reduce the amplitude of these vibrations, rotor 12 includes vibration damping system, is connected to based on use for disappearing
The PZT (piezoelectric transducer) 28 of the device of consuming electric power.PZT (piezoelectric transducer) 28 or piezoelectric patches are the component for including piezoelectric material, piezoelectric material
Deformation can be converted to electric current.Electric energy can be converted mechanical energy into as a result,.PZT (piezoelectric transducer) is polarized, and is generated symbol and taken
Certainly in the charge of its deformation direction and its orientation.PZT (piezoelectric transducer) may include piezo-electricity composite material, such as AFC (activated fibre
Composite material).This material, which can be deformed into, allows PZT (piezoelectric transducer) to be mounted on curved surface.
In order not to interfere air mechanics contour, 28 no-fix of PZT (piezoelectric transducer) is located in drum 12 on blade
On the available surface in portion, it is evenly distributed within the scope of 360 °.PZT (piezoelectric transducer) can be implanted into the cylindrical surface or diameter of rotor 12
To on surface.The rotor may include many components with many groups of PZT (piezoelectric transducer)s 28, they are distributed at round.
Fig. 3 shows the rotor 12 when watching along axis 14 in the past.This is illustrated in associated resonance frequency omegaRUnder, turn
The mode with diameter or the Mode Shape with diameter of son 12.There are three diameters for the Mode Shape tool with diameter.Tool
There is the Mode Shape of diameter to consist essentially of two deformation waves 30, wherein each also has frequencies omegaR.Deformation wave is each other just
It hands over.They are fixed relative to rotor 12.The maximum distortion amplitude of deformation wave 30 deviates relative to each other.Theoretically, these maximum values
It is equal.In fact, they can be different from each other.Mode Shape corresponds to the linear combination of two orthogonality distortion waves 30.
Mode Shape is embodied on rotor 12 by the vibration wave formed.In practice, excitation is relative to rotor 12
Rotation.Due to the combination of two orthogonality distortion waves 30, Mode Shape can be such that rotor 12 overturns.
Due to the symmetry of rotor 12, the phase shift of these deformation waves 30 is 90 °.They generate phase along the circumference of rotor 12
Position variation.The point of the phase change corresponds to vibration nodal point, and in vibration nodal point, rotor 12 will not be undergone and given deformation wave phase
Any displacement or any deformation closed.These referred to as nodal diameter 32 diametrically arrangement, for rotational symmetry
Rotor 12, be evenly distributed within the scope of 360 °.Associated with deformation wave 30 nodal diameter 32 is by with similarity
Line is shown: having the line for the point being arranged close to one another for one in deformation wave, and there is the line for the point being spaced further apart to use
Another in deformation wave.
The Mode Shape further includes shape nodal diameter (shape nodal diameter) (not shown).It include with
The diameter of its each shape just as much.The nodal diameter of the shape corresponds to the position that deformation wave 30 is cancelled out each other.
These shape nodal diameters will not undergo the point of any deformation corresponding to rotor 12.Since the Mode Shape overturns rotor,
So shape nodal diameter also can rotate.
In the present invention, the diameter number used corresponds to the number of Mode Shape.The nodal diameter of Mode Shape is that
The diameter physically observed a bit.
Member based on completion calculates and based on the excitation sequence (the orders of excitation) to structure
Solution identifies the Mode Shape with diameter that can be motivated.Such as it can determine the position of nodal diameter 32 according to the position of rotor blade
It sets.Mode Shape for blade to number and for diameter number equal to the half of lobe numbers, the position of nodal diameter 32
Setting can be between the blades.In this case, Mode Shape or static.When the diameter number of Mode Shape is less than the number of blade
When purpose half, Mode Shape be can rotate.
It can execute by vibration damping system the damping of the Mode Shape with the diameter vibration damping system packet
Include first group of PZT (piezoelectric transducer) 28.They must be positioned according to nodal diameter 32, so that mechanical-electric coupling maximizes.They are positioned
Between nodal diameter 32.This to can avoid offsetting the energy converter, because in the opposite case, same PZT (piezoelectric transducer)
Two regions can generate opposite charge.Because they will not be deformed, nodal region is avoided.For example, static
In the case where Mode Shape, damping system may include twice of the PZT (piezoelectric transducer) 28 that number is equal to diameter number.
The energy converter is evenly distributed within the scope of 360 °, and is similar.They depict concentric with rotor 12
Circle.Since deformation wave 30 is out-phase, so they are substantially sequentially damped by first group of PZT (piezoelectric transducer) 28.Described first
The component of group PZT (piezoelectric transducer) 28 physically extends at least half of circumference range.
In order to the Mode Shape of effectively damping rotary, vibration damping system includes second group of PZT (piezoelectric transducer) 28.The
Two groups can be similar to first group.Second group of PZT (piezoelectric transducer) 28 is arranged between first group of PZT (piezoelectric transducer).Two groups of pressures
Electric transducer 28 is advantageously evenly distributed in the range of same circle.Two groups of PZT (piezoelectric transducer)s 28 can be arranged in axial dipole field
In circle and/or in the circle with different radii.Generally, the PZT (piezoelectric transducer) 28 of damping system occurs from resonance frequency omegaR
Under four times of nodal diameter 32.Second group another benefit is that, can avoid wave amplify between first group of PZT (piezoelectric transducer) 28.
However, the number of PZT (piezoelectric transducer) required for damping system is twice of diameter number, right for still-mode
It is four times of diameter number in rotation mode, this is because two static orthogonal modes must be damped preferably.
In order to ensure the optimum control to two quadrature waves, therefore, it is maximum that PZT (piezoelectric transducer) 28 cannot be only situated in deformation
Place.Therefore, each PZT (piezoelectric transducer) is located at each square wave (squaring) of deformation wave.They occupy deformation square wave
It is most of.It integrates, each group PZT (piezoelectric transducer) 28 substantially depicts more than the circle that they can be delineated 20%, is preferably more
50%, more preferably more 90% circle.
Such structure for good and all and with identical effect can ensure rotation mould to two orthogonal modes and thus
The control of formula.
Fig. 4 is shown provided with the rotor 12 of vibration damping system, and the vibration damping system is based on the piezoelectricity for using shunting
Energy converter.Due to the connection, the invention enables can limit two groups of PZT (piezoelectric transducer)s 28.Each PZT (piezoelectric transducer) and other groups
Two direct borders of PZT (piezoelectric transducer).
According to the present invention, same group of PZT (piezoelectric transducer) 28 is electrically interconnected.In order to gather their electric energy, they are in parallel
Connection.However, two energy converters that direct border gives energy converter " X " can be opposite with the energy converter " X " for each group
Direction on have curved shape.Therefore, some energy converters can through Tensile and others can through compressed, thus generate have
The electric current of distinct symbols.In order to make the electric current provided by each energy converter 28 in same group that there are the same symbol, two borders
Energy converter the pole reversal.It is this reversely to be carried out by means of electrical connection, or based on the piezoelectric material for including by energy converter 28
Natural polarity and carry out.
The group of PZT (piezoelectric transducer) 28 is connected by means of attachment device 34, and the attachment device may include line or rotor
12 structural detail.The attachment device 34 of two groups can be overlapped, and advantageously in intersection point or within the scope of its whole length
Electrical isolation.The attachment device 34 for being exclusively used in identical PZT (piezoelectric transducer) 28 and collector branch is arranged in electrical connector 35
Between (collector branch).The latter can depict circle on rotor.
In order to consume rotor 12 with vibrational energy existing for mechanical type, each group of PZT (piezoelectric transducer) 28 is connected to and is used for
Consume the common circuit 36 of electric energy.This connection method makes that identical consumption circuit 36 and multiple PZT (piezoelectric transducer)s 28 can be gathered.
The present invention utilizes the symmetry of the mode with diameter, wherein 28 groups of each PZT (piezoelectric transducer) symmetrically deform.Every group of piezoelectric energy-conversion
Device 28 becomes coherent power source relative to given deformation.
Fig. 5 shows the circuit for connecting PZT (piezoelectric transducer) 28.It forms closed circuit, and is produced by means of consumption circuit 36
The branch of raw PZT (piezoelectric transducer) 28.Consumption circuit 36 includes that resistor 40 for consuming energy in the form of heat and having closes
The inductor 42 for closing the resonance of circuit, allows to guide energy in circuit.Inductor can be coil 48, preferably mould
Quasi- coil.It should be noted that former-wound coil is passive (passive).
The consumption circuit may include the multiple resistors being connected in series.It may also include multiple inductions of series connection
Device.These identical components can integrate in unitary closed circuit, such as at attachment device 34.In accordance with side of the invention
Method, attachment device 34 can have the natural resistance for consuming energy.
Being connected in parallel for PZT (piezoelectric transducer) 28 can simulate being connected in parallel for the capacitor with capacitor C, they are similar to
Single capacitor with equivalent capacity acts in closed circuit, and is equal to the sum of independent capacitance, because of PZT (piezoelectric transducer)
28 are connected in parallel.
The component of 28 groups of PZT (piezoelectric transducer), resistor 40 and coil 42 forms resonance and damping rlc circuit.Its damped frequency
ωACapacitor C and its inductance L depending on circuit.The frequency is the frequency that the circuit is effective as damper.
The frequency is equal to:
(being indicated with hertz)
Important level of vibration generates under such running speed, and for the running speed, resonance appears in structure
Excitation and natural mode between.Therefore, at these speeds, the use of damper is highly important.
The selection of the size of the different elements of closed circuit by match circuit resonance frequency omegaAWith the critical module to be damped
The demand control of the frequency of formula.Rotor 12, PZT (piezoelectric transducer) 28 and consumption circuit 36 form Mechatronic Systems, the electromechanics system as a result,
System can convert mechanical energy into electric energy, and the mechanical energy can be transmitted to the circuit of consumption energy from blade rotor wheel.
The present invention is convenient for damp low-frequency natural mode by means of shunt circuit, and the shunt circuit can be completely passive
's.In fact, in formula in front, the resonance frequency of circuit and damped frequency thus depend on the capacitor C of circuit.This
A capacitor is bigger, lower for inductance value needed for given frequency.Inductance value is lower, and coil dimension is smaller, therefore it can hold
It changes places and is integrated in mechanical structure.In fact, coil completely simulates member compared with the synthesis inductor based on gyrator principle
Part.Therefore, the present invention makes it possible completely passive embodiment.
For the mode with N number of diameter, the number of PZT (piezoelectric transducer) is 4N, is distributed as being connected to its dedicated shunting
Two groups of 2N energy converters of circuit.Therefore, for given resonance frequency, 2N energy converter is connected in parallel so that making each electricity
The inductor size on road reduces factor 2N relative to damping system, and in damping system, each energy converter is equipped with inductor.This
Outside, it is only necessary to two inductors are provided, rather than four., this corresponds again to the reduction of factor 2N.Therefore, generally, for
Identical effect, this construction is so that can reduce factor 4N for the overall dimensions of inductor2。
Claims (14)
1. rotor (12), including vibration damping system, the vibration damping system are distributed on the rotor with including into round
And it is connected at least one set of PZT (piezoelectric transducer) (28) of at least one consumption circuit (36),
It is characterized in that,
The PZT (piezoelectric transducer) (28) connect so that consume circuit (36) to contain at least two the corresponding of PZT (piezoelectric transducer)
Group is gathered, and at least two PZT (piezoelectric transducer)s in respective sets are connected in parallel, described group or each group of PZT (piezoelectric transducer)
(28) uniformly ditch is distributed on the rotor,
Wherein, the vibration damping system includes two group of at least two PZT (piezoelectric transducer) (28), and described group of angular variation is at all groups
In the uniform ditch of all PZT (piezoelectric transducer)s be distributed on the rotor.
2. rotor (12) according to claim 1, which is characterized in that the rotor can be according to the mode with diameter
It is deformed under the vibration of the vibration shape, the number of described group or each group of PZT (piezoelectric transducer) (28) is equal to the diameter number of the Mode Shape
Twice of purpose.
3. rotor (12) according to claim 2, which is characterized in that the Mode Shape with diameter consists essentially of
Two orthogonality distortion waves (30) with nodal diameter (32), in every case, PZT (piezoelectric transducer) (28) angle are distributed in two
Between two adjacent nodal diameters (32) of a deformation wave (30).
4. rotor (12) according to any one of claims 1 to 3, which is characterized in that the vibration damping system packet
Include it is equal to it is described consumption circuit (36) in corresponding one at least two PZT (piezoelectric transducer) of multiple groups (28) being connected in parallel, each group
The polarity of PZT (piezoelectric transducer) connect into when the PZT (piezoelectric transducer) deforms in the same direction, the PZT (piezoelectric transducer) (28)
The electric current with the same symbol is generated in consumption circuit (36) accordingly.
5. rotor (12) according to any one of claims 1 to 3, which is characterized in that the vibration damping system is only
The polarity of one group of at least two PZT (piezoelectric transducer) (28) including being connected to consumption circuit (36), described group of PZT (piezoelectric transducer) connects
It is connected into when the PZT (piezoelectric transducer) deforms in the same direction, the PZT (piezoelectric transducer) (28) is in the consumption circuit (36)
It is middle to generate the electric current with the same symbol.
6. rotor (12) according to any one of claims 1 to 3, which is characterized in that the rotor can be in basis
Deformed under the vibration of Mode Shape with diameter, the vibration damping system include two groups of PZT (piezoelectric transducer)s (28), described two
Group PZT (piezoelectric transducer) is turned round and out-phase with sub-fraction relative to each other, and the sub-fraction revolution is equal to the mould with diameter
Four times of inverse of the diameter number of the state vibration shape.
7. rotor (12) according to any one of claims 1 to 3, which is characterized in that the consumption circuit or consumption
At least one of circuit (36) includes at least one inductor, to form resonance circuit with the PZT (piezoelectric transducer) being connected in parallel,
At least one of the consumption circuit or consumption circuit (36) substantially combine and shape with the PZT (piezoelectric transducer) (28) of corresponding group
At closed circuit.
8. rotor (12) according to any one of claims 1 to 3, which is characterized in that the consumption circuit or consumption
At least one of circuit (36) does not have external power supply.
9. rotor (12) according to any one of claims 1 to 3, which is characterized in that the rotor has at least one
A resonance frequency omegaR, the consumption circuit (36) is resonance antihunt circuit, the damped frequency ω of the consumption circuitAEqual to will quilt
Rotor (12) resonance frequency omega of dampingR。
10. rotor (12) according to any one of claims 1 to 3, which is characterized in that the rotor is impeller or leaf
Drum.
11. rotor (12) according to any one of claims 1 to 3, which is characterized in that the PZT (piezoelectric transducer) (28)
At least one of be arranged in cylindrical surface or perpendicular on the surface of the rotation axis (14) of the rotor, be located at aerodynamic flow it
Outside.
12. rotor (12) according to any one of claims 1 to 3, which is characterized in that the PZT (piezoelectric transducer) (28)
It is arranged to deform under the stretching/compressing caused by the bending motion as the rotor (12), follows the curved of the shell of the rotor
Song deformation.
13. including the turbine (2) of rotor (12), which is characterized in that the rotor (12) is according to claim 1 to appointing in 12
One and formed, the rotor is the rotor of compressor (4,6) or turbine (10).
14. turbine (2) according to claim 13, which is characterized in that described during the operation in critical speed
Rotor (12) with according to have diameter mode resonance frequency, the number of each group of PZT (piezoelectric transducer) (28) be greater than or
Equal to twice of diameter (32) number of resonance mode.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP13188506.3 | 2013-10-14 | ||
| EP13188506.3A EP2860405B1 (en) | 2013-10-14 | 2013-10-14 | Piezoelectric damper system for axial turbomachine rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104564798A CN104564798A (en) | 2015-04-29 |
| CN104564798B true CN104564798B (en) | 2019-01-15 |
Family
ID=49328438
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410541360.2A Active CN104564798B (en) | 2013-10-14 | 2014-10-14 | Piezo-electric damping system for axial turbine rotor |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US10125794B2 (en) |
| EP (1) | EP2860405B1 (en) |
| CN (1) | CN104564798B (en) |
| CA (1) | CA2866756C (en) |
| RU (1) | RU2602713C2 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10557352B2 (en) * | 2014-09-09 | 2020-02-11 | Rolls-Royce Corporation | Piezoelectric damping rings |
| US10612401B2 (en) * | 2014-09-09 | 2020-04-07 | Rolls-Royce Corporation | Piezoelectric damping rings |
| FR3055758B1 (en) * | 2016-09-08 | 2020-11-27 | Safran Helicopter Engines | AIR INTAKE FLAP CONTROL DEVICE VIA A MULTI-LAYER PIEZOELECTRIC ACTUATOR |
| US10199558B2 (en) * | 2016-10-22 | 2019-02-05 | Michael H. Peters | Piezoelectric power generator |
| RU2691706C2 (en) * | 2017-05-22 | 2019-06-17 | Игорь Викторович Лентов | Operating method of multistage axial machines |
| DE102017119870A1 (en) * | 2017-08-30 | 2019-02-28 | Rolls-Royce Deutschland Ltd & Co Kg | Blade assembly of a turbomachine |
| CN108119603B (en) * | 2017-12-07 | 2019-10-11 | 南京航空航天大学 | A kind of vibration damping loop device based on piezo-electric stack |
| FR3089585B1 (en) * | 2018-12-07 | 2021-09-17 | Safran Helicopter Engines | TURBOMACHINE ROTOR |
| CN109578503B (en) * | 2018-12-11 | 2024-02-13 | 南京航空航天大学 | Fork-type piezoelectric stack vibration damping ring |
| CN110567054B (en) * | 2019-09-02 | 2020-09-22 | 珠海格力电器股份有限公司 | Vibration adjusting assembly, compressor vibration reducing structure and air conditioner |
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| JPS6166544A (en) * | 1984-09-06 | 1986-04-05 | Toshiba Corp | Vibration and noise suppressor |
| US5005353A (en) * | 1986-04-28 | 1991-04-09 | Rolls-Royce Plc | Active control of unsteady motion phenomena in turbomachinery |
| US5370340A (en) * | 1991-11-04 | 1994-12-06 | General Electric Company | Active control of aircraft engine noise using vibrational inputs |
| JPH0861295A (en) * | 1994-08-19 | 1996-03-08 | Ebara Corp | Impeller with vibration damping function |
| US5783898A (en) * | 1996-02-26 | 1998-07-21 | Mcdonnell Douglas Corporation | Piezoelectric shunts for simultaneous vibration reduction and damping of multiple vibration modes |
| US6299410B1 (en) * | 1997-12-26 | 2001-10-09 | United Technologies Corporation | Method and apparatus for damping vibration in turbomachine components |
| CN102223105A (en) * | 2010-04-14 | 2011-10-19 | 南京航空航天大学 | Piezoelectric generator |
| FR2951223B1 (en) * | 2009-10-09 | 2011-12-23 | Snecma | DAMPING OF A ROTARY PIECE BY PIEZOELECTRIC DEVICE DISSIPATIVE SEMI-ACTIVE SWITCHED. |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101501330B (en) * | 2006-08-14 | 2013-05-29 | 罗斯蒙德公司 | Vibration power generation |
-
2013
- 2013-10-14 EP EP13188506.3A patent/EP2860405B1/en active Active
-
2014
- 2014-10-06 CA CA2866756A patent/CA2866756C/en active Active
- 2014-10-14 RU RU2014141132/06A patent/RU2602713C2/en active
- 2014-10-14 US US14/514,100 patent/US10125794B2/en active Active
- 2014-10-14 CN CN201410541360.2A patent/CN104564798B/en active Active
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|---|---|---|---|---|
| JPS6166544A (en) * | 1984-09-06 | 1986-04-05 | Toshiba Corp | Vibration and noise suppressor |
| US5005353A (en) * | 1986-04-28 | 1991-04-09 | Rolls-Royce Plc | Active control of unsteady motion phenomena in turbomachinery |
| US5370340A (en) * | 1991-11-04 | 1994-12-06 | General Electric Company | Active control of aircraft engine noise using vibrational inputs |
| JPH0861295A (en) * | 1994-08-19 | 1996-03-08 | Ebara Corp | Impeller with vibration damping function |
| US5783898A (en) * | 1996-02-26 | 1998-07-21 | Mcdonnell Douglas Corporation | Piezoelectric shunts for simultaneous vibration reduction and damping of multiple vibration modes |
| US6299410B1 (en) * | 1997-12-26 | 2001-10-09 | United Technologies Corporation | Method and apparatus for damping vibration in turbomachine components |
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Also Published As
| Publication number | Publication date |
|---|---|
| RU2014141132A (en) | 2016-05-10 |
| RU2602713C2 (en) | 2016-11-20 |
| US10125794B2 (en) | 2018-11-13 |
| CN104564798A (en) | 2015-04-29 |
| CA2866756A1 (en) | 2015-04-14 |
| EP2860405A1 (en) | 2015-04-15 |
| US20150104295A1 (en) | 2015-04-16 |
| EP2860405B1 (en) | 2016-05-25 |
| CA2866756C (en) | 2019-11-19 |
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